Abstract

The influence of shock/shock and shock-wave/boundary-layer interactions on the flow past two model configurations, representing critical parts of hypersonic vehicles, is examined. The investigation is focused, on the one hand, on the flow field past the windward surface of a reentry vehicle with control surfaces, approximated by a flared hyperboloid, where the influence of high-temperature effects on the interaction is shown. On the other hand, the three-dimensional, turbulent flow field past a blunt fin is discussed.

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